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MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: MH 32 8.7% (mh32-il)
Reynolds number: 100,000
Max Cl/Cd: 53.1 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh32-il-100000-n5.txt
Download as CSV file: xf-mh32-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 32  8.7%                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4284   0.11183   0.10663  -0.0194   1.0000   0.0216
  -9.750  -0.4253   0.10795   0.10280  -0.0208   1.0000   0.0202
  -9.500  -0.4239   0.10374   0.09863  -0.0225   1.0000   0.0186
  -9.000  -0.4212   0.09442   0.08940  -0.0280   1.0000   0.0153
  -8.750  -0.4211   0.09042   0.08545  -0.0292   1.0000   0.0150
  -8.500  -0.4205   0.08687   0.08196  -0.0304   1.0000   0.0147
  -8.250  -0.4219   0.08297   0.07813  -0.0320   1.0000   0.0145
  -8.000  -0.4242   0.07933   0.07457  -0.0334   1.0000   0.0143
  -7.750  -0.4300   0.07560   0.07092  -0.0349   1.0000   0.0141
  -7.500  -0.4357   0.07169   0.06709  -0.0371   1.0000   0.0139
  -7.250  -0.4402   0.06697   0.06241  -0.0401   1.0000   0.0137
  -7.000  -0.4434   0.06270   0.05814  -0.0417   1.0000   0.0134
  -6.750  -0.4469   0.05815   0.05354  -0.0428   1.0000   0.0133
  -6.500  -0.4486   0.05404   0.04933  -0.0429   1.0000   0.0131
  -6.250  -0.4485   0.04990   0.04502  -0.0425   1.0000   0.0128
  -6.000  -0.4457   0.04567   0.04054  -0.0420   1.0000   0.0127
  -5.750  -0.4393   0.04163   0.03618  -0.0413   1.0000   0.0126
  -5.500  -0.4293   0.03783   0.03198  -0.0405   1.0000   0.0128
  -5.250  -0.4157   0.03443   0.02810  -0.0395   1.0000   0.0138
  -5.000  -0.3834   0.03102   0.02398  -0.0413   0.9954   0.0150
  -4.750  -0.3528   0.02748   0.01985  -0.0430   0.9907   0.0164
  -4.500  -0.3205   0.02496   0.01690  -0.0444   0.9860   0.0173
  -4.250  -0.2858   0.02288   0.01447  -0.0458   0.9821   0.0187
  -4.000  -0.2544   0.02119   0.01246  -0.0464   0.9767   0.0205
  -3.750  -0.2202   0.02001   0.01102  -0.0475   0.9718   0.0249
  -3.500  -0.1870   0.01863   0.00959  -0.0489   0.9673   0.0319
  -3.250  -0.1557   0.01758   0.00842  -0.0495   0.9609   0.0485
  -3.000  -0.1210   0.01635   0.00745  -0.0512   0.9564   0.0995
  -2.750  -0.0914   0.01536   0.00700  -0.0521   0.9497   0.2195
  -2.500  -0.0585   0.01453   0.00674  -0.0535   0.9442   0.3737
  -2.250  -0.0282   0.01389   0.00655  -0.0540   0.9379   0.5211
  -2.000   0.0010   0.01340   0.00646  -0.0537   0.9313   0.6567
  -1.750   0.0300   0.01307   0.00638  -0.0529   0.9246   0.7742
  -1.500   0.0704   0.01284   0.00623  -0.0543   0.9192   0.8863
  -1.250   0.1346   0.01265   0.00585  -0.0613   0.9169   0.9745
  -1.000   0.1766   0.01259   0.00559  -0.0643   0.9093   1.0000
  -0.750   0.2104   0.01253   0.00537  -0.0654   0.9010   1.0000
  -0.500   0.2374   0.01252   0.00521  -0.0652   0.8896   1.0000
  -0.250   0.2648   0.01251   0.00508  -0.0650   0.8783   1.0000
   0.000   0.2925   0.01250   0.00497  -0.0648   0.8669   1.0000
   0.250   0.3200   0.01248   0.00486  -0.0645   0.8553   1.0000
   0.500   0.3471   0.01247   0.00476  -0.0641   0.8430   1.0000
   0.750   0.3736   0.01246   0.00468  -0.0635   0.8296   1.0000
   1.000   0.3995   0.01245   0.00462  -0.0629   0.8150   1.0000
   1.250   0.4254   0.01245   0.00457  -0.0621   0.7994   1.0000
   1.500   0.4514   0.01246   0.00454  -0.0614   0.7831   1.0000
   1.750   0.4777   0.01246   0.00449  -0.0608   0.7664   1.0000
   2.000   0.5034   0.01250   0.00449  -0.0600   0.7480   1.0000
   2.250   0.5291   0.01255   0.00450  -0.0593   0.7286   1.0000
   2.500   0.5550   0.01262   0.00452  -0.0585   0.7087   1.0000
   2.750   0.5805   0.01272   0.00462  -0.0578   0.6869   1.0000
   3.000   0.6059   0.01284   0.00470  -0.0570   0.6641   1.0000
   3.250   0.6312   0.01300   0.00480  -0.0562   0.6406   1.0000
   3.500   0.6562   0.01320   0.00494  -0.0554   0.6158   1.0000
   3.750   0.6809   0.01343   0.00516  -0.0546   0.5899   1.0000
   4.000   0.7053   0.01369   0.00537  -0.0537   0.5631   1.0000
   4.250   0.7294   0.01399   0.00562  -0.0529   0.5356   1.0000
   4.500   0.7531   0.01431   0.00590  -0.0520   0.5070   1.0000
   4.750   0.7766   0.01467   0.00622  -0.0511   0.4776   1.0000
   5.000   0.7997   0.01506   0.00662  -0.0502   0.4471   1.0000
   5.250   0.8225   0.01549   0.00701  -0.0492   0.4160   1.0000
   5.500   0.8448   0.01597   0.00744  -0.0483   0.3843   1.0000
   5.750   0.8668   0.01648   0.00792  -0.0473   0.3519   1.0000
   6.000   0.8883   0.01704   0.00844  -0.0463   0.3193   1.0000
   6.250   0.9093   0.01767   0.00901  -0.0453   0.2877   1.0000
   6.500   0.9301   0.01833   0.00971  -0.0443   0.2554   1.0000
   6.750   0.9503   0.01906   0.01040  -0.0432   0.2239   1.0000
   7.000   0.9698   0.01987   0.01115  -0.0421   0.1933   1.0000
   7.250   0.9889   0.02073   0.01196  -0.0410   0.1615   1.0000
   7.500   1.0072   0.02169   0.01286  -0.0398   0.1310   1.0000
   7.750   1.0245   0.02277   0.01386  -0.0386   0.1031   1.0000
   8.000   1.0412   0.02393   0.01501  -0.0372   0.0804   1.0000
   8.250   1.0555   0.02534   0.01639  -0.0355   0.0638   1.0000
   8.500   1.0691   0.02680   0.01785  -0.0338   0.0489   1.0000
   8.750   1.0799   0.02849   0.01965  -0.0318   0.0392   1.0000
   9.000   1.0925   0.02995   0.02127  -0.0300   0.0304   1.0000
   9.250   1.1006   0.03186   0.02334  -0.0276   0.0254   1.0000
   9.500   1.1092   0.03350   0.02509  -0.0256   0.0205   1.0000
   9.750   1.1109   0.03580   0.02753  -0.0227   0.0182   1.0000
  10.000   1.1165   0.03801   0.03000  -0.0202   0.0165   1.0000
  10.250   1.1215   0.04020   0.03242  -0.0180   0.0150   1.0000
  10.500   1.1245   0.04228   0.03467  -0.0161   0.0137   1.0000
  10.750   1.1230   0.04462   0.03713  -0.0143   0.0124   1.0000
  11.000   1.1176   0.04803   0.04071  -0.0127   0.0116   1.0000
  11.250   1.1168   0.05087   0.04387  -0.0115   0.0111   1.0000
  11.500   1.1123   0.05429   0.04759  -0.0106   0.0107   1.0000
  11.750   1.1046   0.05820   0.05178  -0.0103   0.0105   1.0000
  12.000   1.0942   0.06258   0.05644  -0.0106   0.0103   1.0000
  12.250   1.0825   0.06734   0.06145  -0.0118   0.0103   1.0000
  12.500   1.0683   0.07283   0.06718  -0.0139   0.0103   1.0000
  12.750   1.0532   0.07890   0.07347  -0.0169   0.0102   1.0000
  13.000   1.0364   0.08579   0.08057  -0.0209   0.0103   1.0000
  13.250   1.0196   0.09327   0.08823  -0.0255   0.0104   1.0000
  13.500   1.0021   0.10154   0.09666  -0.0308   0.0106   1.0000
  13.750   0.9851   0.11033   0.10557  -0.0364   0.0107   1.0000
  14.000   0.9684   0.11964   0.11498  -0.0421   0.0110   1.0000
  14.250   0.9524   0.12934   0.12473  -0.0479   0.0112   1.0000
  14.500   0.9390   0.13862   0.13404  -0.0530   0.0115   1.0000
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